US6306515B1 - Thermal barrier and overlay coating systems comprising composite metal/metal oxide bond coating layers - Google Patents

Thermal barrier and overlay coating systems comprising composite metal/metal oxide bond coating layers Download PDF

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US6306515B1
US6306515B1 US09/133,763 US13376398A US6306515B1 US 6306515 B1 US6306515 B1 US 6306515B1 US 13376398 A US13376398 A US 13376398A US 6306515 B1 US6306515 B1 US 6306515B1
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thermal barrier
coating layer
mcraly
coating system
metal oxide
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John G. Goedjen
Stephen M. Sabol
Kelly M. Sloan
Steven J. Vance
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Siemens Energy Inc
CBS Corp
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Siemens Westinghouse Power Corp
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Priority to US09/133,763 priority Critical patent/US6306515B1/en
Application filed by Siemens Westinghouse Power Corp filed Critical Siemens Westinghouse Power Corp
Assigned to SIEMENS WESTINGHOUSE POWER CORPORATION reassignment SIEMENS WESTINGHOUSE POWER CORPORATION NUNC PRO TUNC EFFECTIVE DATE AUGUST 19, 1998 Assignors: CBS CORPORATION (FORMERLY KNOWN AS WESTINGHOUSE ELECTRIC CORPORATION)
Priority to EP99114404A priority patent/EP0979881B1/en
Priority to DE69903699T priority patent/DE69903699T2/en
Priority to JP11224936A priority patent/JP2000094574A/en
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    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/325—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with layers graded in composition or in physical properties
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S428/00—Stock material or miscellaneous articles
    • Y10S428/922—Static electricity metal bleed-off metallic stock
    • Y10S428/9335—Product by special process
    • Y10S428/937—Sprayed metal

Definitions

  • the present invention generally describes multilayer coating systems comprising a composite metal/metal oxide bond coating layer.
  • the coating systems of the present invention may be used in gas turbines.
  • superalloys, MCrAlY bond coatings, and overlay coatings often contain elements such as aluminum or chromium for oxidation and corrosion resistance.
  • elements such as aluminum or chromium for oxidation and corrosion resistance.
  • One or more of these elements form a thermally grown oxide (TGO) layer on the surface which acts as a barrier to further oxidation and corrosion.
  • TGO thermally grown oxide
  • alloying elements like Ti, W, Ta or Hf diffuse up from the substrate and into the thermally grown oxide layer.
  • impurities degrade the thermally grown oxide layer and reduce its protective ability.
  • thermal barrier coating systems and overlay coating systems that reduce interdiffusion of elements between the substrate and the bond coat in order to increase the life of the systems.
  • the present invention is directed to these. as well as other, important ends.
  • the present invention generally describes multilayer thermal barrier coating systems comprising a thermal barrier coating, layer, a high density metallic bond coating layer, a composite metal/metal oxide bond coating layer and a substrate.
  • the thermal barrier coating systems further comprise a thermally grown oxide layer that forms during manufacture and/or service.
  • the present invention also generally describes overlay coating systems comprising a high density metallic bond coating layer, a composite metal/metal oxide bond coating layer and a substrate.
  • the present invention also describes methods of making multilayer thermal barrier coating system comprising depositing a composite metal/metal oxide bond coating layer on a substrate; depositing a high density metallic bond coating layer on the composite metal and oxide bond coating layer; and depositing a thermal barrier coating layer on the high density metallic bond coating layer.
  • the method further comprises heating the multilayer thermal barrier coating system to produce a thermally grown oxide layer between the thermal barrier coating layer and the high density metallic bond coating layer.
  • the present invention also describes methods of making multilayer overlay coating system comprising depositing a composite metal/metal oxide bond coating layer on a substrate, and depositing a high density metallic bond coating layer on the composite metal/metal oxide bond coating layer.
  • FIG. 1 is a cross-sectional view of multilayer thermal barrier coating systems of the present invention comprising a thermal barrier coating layer, a high density metallic bond coating layer (MCrAlY), a composite metal/metal oxide bond coating layer and a substrate.
  • MrAlY high density metallic bond coating layer
  • FIG. 1 is a cross-sectional view of multilayer thermal barrier coating systems of the present invention comprising a thermal barrier coating layer, a high density metallic bond coating layer (MCrAlY), a composite metal/metal oxide bond coating layer and a substrate.
  • MrAlY high density metallic bond coating layer
  • FIG. 2 is a cross-sectional view of multilayer thermal barrier coating systems of the present invention comprising a thermal barrier coating layer, a thermally grown oxide layer, a high density metallic bond coating layer (MCrAlY), a composite metal/metal oxide bond coating layer and a substrate after thermal bond coating failure as a result of thermal exposure.
  • FIG. 3 is a cross-sectional view of multilayer thermal barrier coating system of the current state of the art comprising a thermal barrier coating layer, a thermally grown oxide layer, a high density metallic bond coating layer (MCrAlY), and a substrate WITHOUT the composite metal/metal oxide bond coating layer after thermal bond coating failure as a result of thermal exposure.
  • the present invention generally describes multilayer thermal barrier coating systems for high temperature, hot section, turbine applications including, but not limited to, blades, vanes, combustors, and transitions.
  • the conventional approach to applying thermal sprayed MCrAlY bond coat or overlay coating is to minimize the amount of oxides in the layer by adjusting processing parameters, controlling the surrounding atmosphere, such as by shrouding with argon, or by spraying in a low pressure or vacuum chamber.
  • LPPS low pressure plasma sprayed
  • HVOF high velocity oxygen fuel
  • the multilayer thermal barrier coating systems of the present invention comprise a thermal barrier coating layer 10 , a thermally grown oxide layer 18 , a high density metallic bond coating layer 12 , a composite metal/metal oxide bond coating layer 14 and a substrate 16 .
  • the thermal barrier coating layer 10 is generally an 8% yttrium stabilized zirconia layer that is applied by methods known to one skilled in the art, such as air plasma spraying or physical vapor deposition.
  • the thermal barrier coating layer 10 may also be comprised of magnesia stabilized zirconia, ceria stabilized zirconia, scandia stabilized zirconia or other ceramic with low conductivity.
  • the thermal barrier coating layer 10 is typically present at a thickness of about 5-20 mils.
  • the thermally grown oxide layer 18 (not shown in FIG. 1) is established during manufacturing and/or service exposure and is typically comprised of aluminum oxide.
  • the thermally grown oxide layer 18 grows continuously during the service of the component due to exposure to high temperature oxidizing environments. This growth has been observed to be anywhere from 0 to 15 micrometers thick. More typical, however, is 0 to 10 micrometers thick.
  • the formation of the thermally grown oxide layer 18 is initiated during the coating process itself and provides an oxide surface for the columnar thermal barrier coating layer 10 growth.
  • the temperatures involved are those consistent with current industrial practice for thermal barrier coating deposition and temperatures and times associated with engine operation. Generally, temperatures in excess of 1400 degrees F. are necessary for substantial thermally grown oxide layer 18 formation.
  • the high density metallic bond coating layer 12 is generally an MCrAlY alloy deposited by methods known to one skilled in the art, such as high velocity oxygen fuel or low pressure plasma spray techniques.
  • a typical form of MCrAlY is where M is nickel and/or cobalt and Y is yttrium.
  • additional alloying elements have been added to the mix including rhenium, platinum, tungsten, and other transition metals. NiCoCrAlY's and CoNiCrAlY's are by far the most common.
  • the high density metalic bond coating layer, or MCrAlY layer 12 is typically about 4-10 mils thick unless a particular process restriction requires thicker coatings whereby the metallic bond coating layer 12 accordingly will be thicker.
  • the MCrAlY is typically thinner and may be found at about 2-5 mils thick.
  • the dense MCrAlY layer 12 comprises 50-90% of the total bond coat thickness (both layers) and the composite metal/metal oxide layer 14 comprises 10-50% of the coating thickness. More preferably, the MCrAlY layer 12 comprises 70% of the total bond coat thickness (both layers) and the composite metal/metal oxide layer 14 comprises the other 30% of the coating thickness.
  • the composite metal/metal oxide layer 14 acts as a diffusion barrier.
  • the layer is deposited using methods known to one skilled in the art, such as air plasma spray techniques which can be made to produce a lamellar structure of metal/metal oxide layers 14 which act as a diffusion barrier.
  • This composite metal/metal oxide layer 14 can be formed from any MCrAlY that can be made or is commercially available.
  • the structure of the composite metal/metal oxide layer 14 of the current invention is formed by the insitu oxidation of MCrAlY particles which occurs during air plasma spray by the reaction of the surface of the molten MCrAlY droplet with oxygen in the air.
  • the objectives set forth in this invention can be accomplished by thermal spray co-deposition of ceramic (alumina) and MCrAlY where both powders are fed into the plasma gun either simultaneously or sequentially to build up an alternating layer, or by alternating deposition of thin layers followed by oxidation heat treatments between gun passes such that the diffusion barrier layer is made up of alternating metal-ceramic layers where the layers are continuous or disrupted.
  • substrate 16 refers to the metal component onto which thermal barrier coating systems are applied. This is typically a nickel or cobalt based superalloy such as IN738 made by Inco Alloys International, Inc. More specifically, in a combustion turbine system, the substrate 16 is any hot gas path component including combustors, transitions, vanes, blades, and seal segments.
  • FIGS. 2 and 3 illustrate the advantage of using the composite metal/metal oxide layer 14 of the present invention between the MCrAlY bond coat layer 12 and the superalloy substrate 16 .
  • the coating in FIG. 2 contains a composite metal/metal oxide layer 14 whereas the coating in FIG. 3 does not. Both coatings have been exposed to elevated temperatures in air for 2500 hours.
  • FIG. 2 shows the superalloy substrate 16 , the metal/metal oxide layer 14 , the MCrAlY bond coat layer 12 , the thermally grown oxide layer 18 , and a small amount of residual thermal barrier coating layer 10 after thermal bond coat failure.
  • FIG. 3 shows the superalloy substrate 16 , the MCrAlY bond coat layer 12 , the thermally grown oxide layer 18 , and a small amount of residual thermal bond coat layer 10 after thermal bond coat failure.
  • the phase visible in the MCrAlY bond coat layer 12 is beta nickel aluminide 22 (NiAl).
  • Beta nickel aluminide 22 is the source of the aluminum responsible for forming a dense coherent thermally grown oxide layer 18 (Al 2 O 3 ) which forms during service and is necessary for good oxidation resistance. Aluminum is consumed in the formation of the thermally grown oxide layer 18 and by the diffusion of aluminum into the substrate 16 material.
  • FIG. 2 shows substantially more beta nickel aluminide 22 present in FIG. 2 (containing the composite metal/metal oxide intermediate layer 14 ) than is present in FIG. 3 .
  • FIG. 3 shows two beta depleted zones 20 within the MCrAlY bond coat in FIG. 3 —one adjacent to the substrate 16 superalloy due to interdiffusion and one adjacent to the thermally grown oxide layer 18 due to oxidation.
  • an air plasma sprayed bond coating has historically proven to exhibit inferior performance relative to a low pressure plasma sprayed bond coating.
  • the combination of an air plasma sprayed bond coating to act as a diffusion barrier, and a high density low pressure plasma sprayed or high velocity oxygen fuel bond coating to promote formation of a dense, adherent protective alumina layer offers an improvement over the current single layer bond coating system.
  • the oxidation of the low pressure plasma sprayed coating could further be improved through surface modification, such as aluminizing, platinum aluminizing or other surface modification techniques.

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Abstract

The present invention generally describes multilayer coating systems comprising a composite metal/metal oxide bond coat layer. The coating systems may be used in gas turbines.

Description

GOVERNMENT INTEREST
This invention was made with government support under Contract No. DE-AC05-950R22242, awarded by the United States Department of Energy. The government has certain rights in this invention.
FIELD OF THE INVENTION
The present invention generally describes multilayer coating systems comprising a composite metal/metal oxide bond coating layer. The coating systems of the present invention may be used in gas turbines.
BACKGROUND OF THE INVENTION
In gas turbine applications, superalloys, MCrAlY bond coatings, and overlay coatings often contain elements such as aluminum or chromium for oxidation and corrosion resistance. One or more of these elements form a thermally grown oxide (TGO) layer on the surface which acts as a barrier to further oxidation and corrosion. Over time, alloying elements like Ti, W, Ta or Hf diffuse up from the substrate and into the thermally grown oxide layer. Such impurities degrade the thermally grown oxide layer and reduce its protective ability. There can also be a significant loss of aluminum via diffusion from the bond coat into the substrate, thereby reducing the aluminum reservoir required to maintain the protective layer.
There is a need in the art for thermal barrier coating systems and overlay coating systems that reduce interdiffusion of elements between the substrate and the bond coat in order to increase the life of the systems. The present invention is directed to these. as well as other, important ends.
SUMMARY OF THE INVENTION
The present invention generally describes multilayer thermal barrier coating systems comprising a thermal barrier coating, layer, a high density metallic bond coating layer, a composite metal/metal oxide bond coating layer and a substrate. The thermal barrier coating systems further comprise a thermally grown oxide layer that forms during manufacture and/or service.
The present invention also generally describes overlay coating systems comprising a high density metallic bond coating layer, a composite metal/metal oxide bond coating layer and a substrate.
The present invention also describes methods of making multilayer thermal barrier coating system comprising depositing a composite metal/metal oxide bond coating layer on a substrate; depositing a high density metallic bond coating layer on the composite metal and oxide bond coating layer; and depositing a thermal barrier coating layer on the high density metallic bond coating layer. The method further comprises heating the multilayer thermal barrier coating system to produce a thermally grown oxide layer between the thermal barrier coating layer and the high density metallic bond coating layer.
The present invention also describes methods of making multilayer overlay coating system comprising depositing a composite metal/metal oxide bond coating layer on a substrate, and depositing a high density metallic bond coating layer on the composite metal/metal oxide bond coating layer.
These and other aspects of the present invention will become clearer from the following detailed description.
BRIEF DESCRIPTION OF THE FIGURES
FIG. 1 is a cross-sectional view of multilayer thermal barrier coating systems of the present invention comprising a thermal barrier coating layer, a high density metallic bond coating layer (MCrAlY), a composite metal/metal oxide bond coating layer and a substrate.
FIG. 2 is a cross-sectional view of multilayer thermal barrier coating systems of the present invention comprising a thermal barrier coating layer, a thermally grown oxide layer, a high density metallic bond coating layer (MCrAlY), a composite metal/metal oxide bond coating layer and a substrate after thermal bond coating failure as a result of thermal exposure.
FIG. 3 is a cross-sectional view of multilayer thermal barrier coating system of the current state of the art comprising a thermal barrier coating layer, a thermally grown oxide layer, a high density metallic bond coating layer (MCrAlY), and a substrate WITHOUT the composite metal/metal oxide bond coating layer after thermal bond coating failure as a result of thermal exposure.
DETAILED DESCRIPTION OF THE INVENTION
The present invention generally describes multilayer thermal barrier coating systems for high temperature, hot section, turbine applications including, but not limited to, blades, vanes, combustors, and transitions.
The conventional approach to applying thermal sprayed MCrAlY bond coat or overlay coating is to minimize the amount of oxides in the layer by adjusting processing parameters, controlling the surrounding atmosphere, such as by shrouding with argon, or by spraying in a low pressure or vacuum chamber. The combination of an air plasma sprayed MCrAlY bond coating, with intentionally incorporated oxide, acts as a chemical diffusion barrier between the substrate and the MCrAlY coating. The addition of a second low pressure plasma sprayed (LPPS) or high velocity oxygen fuel (HVOF) bond coating layer, above the air plasma sprayed (APS) diffusion barrier, provides a platform for formation of a slow-growing, adherent oxide layer.
Referring to FIGS. 1, 2, and 3, the multilayer thermal barrier coating systems of the present invention comprise a thermal barrier coating layer 10, a thermally grown oxide layer 18, a high density metallic bond coating layer 12, a composite metal/metal oxide bond coating layer 14 and a substrate 16.
The thermal barrier coating layer 10 is generally an 8% yttrium stabilized zirconia layer that is applied by methods known to one skilled in the art, such as air plasma spraying or physical vapor deposition. The thermal barrier coating layer 10, however, may also be comprised of magnesia stabilized zirconia, ceria stabilized zirconia, scandia stabilized zirconia or other ceramic with low conductivity. The thermal barrier coating layer 10 is typically present at a thickness of about 5-20 mils.
The thermally grown oxide layer 18 (not shown in FIG. 1) is established during manufacturing and/or service exposure and is typically comprised of aluminum oxide. The thermally grown oxide layer 18 grows continuously during the service of the component due to exposure to high temperature oxidizing environments. This growth has been observed to be anywhere from 0 to 15 micrometers thick. More typical, however, is 0 to 10 micrometers thick. In the case of EB-PVD TBC ceramic top coats, the formation of the thermally grown oxide layer 18 is initiated during the coating process itself and provides an oxide surface for the columnar thermal barrier coating layer 10 growth. The temperatures involved are those consistent with current industrial practice for thermal barrier coating deposition and temperatures and times associated with engine operation. Generally, temperatures in excess of 1400 degrees F. are necessary for substantial thermally grown oxide layer 18 formation.
The high density metallic bond coating layer 12 is generally an MCrAlY alloy deposited by methods known to one skilled in the art, such as high velocity oxygen fuel or low pressure plasma spray techniques. A typical form of MCrAlY is where M is nickel and/or cobalt and Y is yttrium. In addition, there are numerous modifications where additional alloying elements have been added to the mix including rhenium, platinum, tungsten, and other transition metals. NiCoCrAlY's and CoNiCrAlY's are by far the most common. For most industrial gas turbine applications, the high density metalic bond coating layer, or MCrAlY layer 12 is typically about 4-10 mils thick unless a particular process restriction requires thicker coatings whereby the metallic bond coating layer 12 accordingly will be thicker. For aero applications, the MCrAlY is typically thinner and may be found at about 2-5 mils thick.
In a preferred embodiment of this invention, the dense MCrAlY layer 12 comprises 50-90% of the total bond coat thickness (both layers) and the composite metal/metal oxide layer 14 comprises 10-50% of the coating thickness. More preferably, the MCrAlY layer 12 comprises 70% of the total bond coat thickness (both layers) and the composite metal/metal oxide layer 14 comprises the other 30% of the coating thickness.
The composite metal/metal oxide layer 14 acts as a diffusion barrier. Preferably, the layer is deposited using methods known to one skilled in the art, such as air plasma spray techniques which can be made to produce a lamellar structure of metal/metal oxide layers 14 which act as a diffusion barrier. This composite metal/metal oxide layer 14 can be formed from any MCrAlY that can be made or is commercially available.
The structure of the composite metal/metal oxide layer 14 of the current invention is formed by the insitu oxidation of MCrAlY particles which occurs during air plasma spray by the reaction of the surface of the molten MCrAlY droplet with oxygen in the air. There are, however, other means of establishing the composite metal/metal oxide 14 are feasible. For example, the objectives set forth in this invention can be accomplished by thermal spray co-deposition of ceramic (alumina) and MCrAlY where both powders are fed into the plasma gun either simultaneously or sequentially to build up an alternating layer, or by alternating deposition of thin layers followed by oxidation heat treatments between gun passes such that the diffusion barrier layer is made up of alternating metal-ceramic layers where the layers are continuous or disrupted.
The term “substrate” 16 refers to the metal component onto which thermal barrier coating systems are applied. This is typically a nickel or cobalt based superalloy such as IN738 made by Inco Alloys International, Inc. More specifically, in a combustion turbine system, the substrate 16 is any hot gas path component including combustors, transitions, vanes, blades, and seal segments.
FIGS. 2 and 3 illustrate the advantage of using the composite metal/metal oxide layer 14 of the present invention between the MCrAlY bond coat layer 12 and the superalloy substrate 16. The coating in FIG. 2 contains a composite metal/metal oxide layer 14 whereas the coating in FIG. 3 does not. Both coatings have been exposed to elevated temperatures in air for 2500 hours.
Specifically, FIG. 2 shows the superalloy substrate 16, the metal/metal oxide layer 14, the MCrAlY bond coat layer 12, the thermally grown oxide layer 18, and a small amount of residual thermal barrier coating layer 10 after thermal bond coat failure. FIG. 3 shows the superalloy substrate 16, the MCrAlY bond coat layer 12, the thermally grown oxide layer 18, and a small amount of residual thermal bond coat layer 10 after thermal bond coat failure. The phase visible in the MCrAlY bond coat layer 12 is beta nickel aluminide 22 (NiAl). Beta nickel aluminide 22 is the source of the aluminum responsible for forming a dense coherent thermally grown oxide layer 18 (Al2O3) which forms during service and is necessary for good oxidation resistance. Aluminum is consumed in the formation of the thermally grown oxide layer 18 and by the diffusion of aluminum into the substrate 16 material.
By comparison, it is readily apparent that there is substantially more beta nickel aluminide 22 present in FIG. 2 (containing the composite metal/metal oxide intermediate layer 14) than is present in FIG. 3. It is also readily apparent that in FIG. 2 there is only one beta depleted zone 20 within the MCrAlY bond coat due to oxidation. In contrast, FIG. 3 shows two beta depleted zones 20 within the MCrAlY bond coat in FIG. 3—one adjacent to the substrate 16 superalloy due to interdiffusion and one adjacent to the thermally grown oxide layer 18 due to oxidation. Without intending to be bound by a theory of the invention, the greater retention of beta nickel aluminide 22 in FIG. 2 is believed to be due to the aluminum oxide particles in the composite metal/metal oxide layer 14 acting as a physical barrier to aluminum diffusion into the superalloy substrate 16. Thus, the presence of the composite metal/metal oxide layer 14 retains beta nickel aluminide 22 in the MCrAlY bond coat layer 12. As a result, a longer coating life is expected.
The use of an air plasma sprayed bond coating has historically proven to exhibit inferior performance relative to a low pressure plasma sprayed bond coating. The combination of an air plasma sprayed bond coating to act as a diffusion barrier, and a high density low pressure plasma sprayed or high velocity oxygen fuel bond coating to promote formation of a dense, adherent protective alumina layer offers an improvement over the current single layer bond coating system. The oxidation of the low pressure plasma sprayed coating could further be improved through surface modification, such as aluminizing, platinum aluminizing or other surface modification techniques.
The teaching of the present invention as it relates to multilayer thermal barrier coatings are identical to multilayer overlay coating systems with one exception; in multilayer overlay coating systems the thermal barrier coating layer (1) is not present. In all other respects, the inventions are the same.
Various modifications of the invention in addition to those shown and described herein will be apparent to one skilled in the art from the foregoing description. Such modifications are also intended to fall within the scope of the appended claims.

Claims (14)

What is claimed is:
1. A multilayer thermal barrier coating system comprising a thermal barrier coating layer deposited upon a high density metallic bond coating layer, the high density metallic bond coating layer deposited upon a diffusion resistant composite MCrAlY/metal oxide bond coating layer, and the composite MCrAlY/metal oxide bond coating layer deposited upon a substrate, wherein said diffusion resistance is provided by a method of deposition in which MCrAlY droplets become heavily decorated with oxides at the splat boundary during the deposition process.
2. The thermal barrier coating system of claim 1, further comprising a thermally grown oxide layer dispersed between the thermal barrier coating layer and the high density metallic bond coating layer.
3. Th e thermal barrier coating system of claim 1, wherein the thermal barrier coating layer comprises a low conductivity ceramic layer.
4. The thermal barrier coating system of claim 3, wherein the low conductivity ceramic layer comprises zirconia stabilized with at least one of yttria, scandia, magnesia, ceria, or a combination thereof.
5. The thermal barrier coating system of claim 1, wherein the high density metallic bond coating layer comprises a MCrAlY alloy, wherein M is at least one of Co, Ni, Fe or a combination thereof.
6. The thermal barrier coating system of claim 1, wherein the composite metal/metal oxide bond coating layer comprises a n MCrAlY and aluminum, oxide.
7. The thermal barrier coating system of claim 1, wherein the substrate comprises a cobalt based superalloy.
8. The thermal barrier coating system of claim 1, wherein the substrate comprises a nickel based superalloy.
9. The thermal barrier coating system of claim 2, wherein the thermally grown oxide layer comprises aluminum oxide.
10. A multilayer overlay coating system comprising a high density metallic bond coating layer deposited upon a diffusion resistant composite MCrAlY/metal oxide bond coating layer, the composite MCrAlY/metal oxide bond coating layer deposited upon a substrate, wherein said diffusion resistance is provided by a method of deposition in which MCrAlY droplets become heavily decorated with oxides at the splat boundary during the deposition process.
11. The overlay coating system of claim 10, wherein the high density metallic bond coating layer comprises a MCrAlY alloy, wherein M is at least one of Co, Ni, Fe or a combination thereof.
12. The overlay coating system of claim 10, wherein the composite metal/metal oxide bond coating layer comprises an MCrAlY and aluminum oxide.
13. The overlay coating system of claim 10, wherein the substrate comprises a cobalt based superalloy.
14. The overlay coating system of claim 10, wherein the substrate comprises a nickel based superalloy.
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Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030175633A1 (en) * 2002-03-15 2003-09-18 Whittenberger William A. Catalytic combustor with improved light-off characteristics
US6649559B2 (en) * 2000-08-12 2003-11-18 Dmc2 Degussa Metals Catalysts Cerdec Ag Supported metal membrane, a process for its preparation and use
US20040021240A1 (en) * 2002-07-31 2004-02-05 Hancun Chen Ceramic manufacture for a composite ion transport membrane
US20040095070A1 (en) * 2002-11-14 2004-05-20 General Electric Company Heat shield design for arc tubes
US20040151839A1 (en) * 2003-01-06 2004-08-05 Shinya Miyaji Sprayed coating and production method for the same
US6793968B1 (en) * 1999-03-04 2004-09-21 Siemens Aktiengesellschaft Method and device for coating a product
US20040209110A1 (en) * 2003-04-18 2004-10-21 General Electric Company Nickel aluminide coating and coating systems formed therewith
US20050003227A1 (en) * 2002-01-10 2005-01-06 Alstom Technology Ltd MCrAIY bond coating and method of depositing said MCrAIY bond coating
US20050042461A1 (en) * 2003-08-18 2005-02-24 Honeywell International Inc. Diffusion barrier coating for si-based components
US20050079368A1 (en) * 2003-10-08 2005-04-14 Gorman Mark Daniel Diffusion barrier and protective coating for turbine engine component and method for forming
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Citations (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3928026A (en) * 1974-05-13 1975-12-23 United Technologies Corp High temperature nicocraly coatings
US4248940A (en) * 1977-06-30 1981-02-03 United Technologies Corporation Thermal barrier coating for nickel and cobalt base super alloys
US4446199A (en) 1982-07-30 1984-05-01 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Overlay metallic-cermet alloy coating systems
US4451496A (en) 1982-07-30 1984-05-29 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Coating with overlay metallic-cermet alloy systems
US4471017A (en) 1981-09-23 1984-09-11 Battelle-Institut E.V. High-temperature and thermal-shock-resistant thermally insulating coatings on the basis of ceramic materials
US4481237A (en) * 1981-12-14 1984-11-06 United Technologies Corporation Method of applying ceramic coatings on a metallic substrate
US4503130A (en) 1981-12-14 1985-03-05 United Technologies Corporation Prestressed ceramic coatings
EP0340791A2 (en) 1988-05-06 1989-11-08 Hitachi, Ltd. Ceramics-coated heat resisting alloy member
US5209645A (en) 1988-05-06 1993-05-11 Hitachi, Ltd. Ceramics-coated heat resisting alloy member
US5305726A (en) * 1992-09-30 1994-04-26 United Technologies Corporation Ceramic composite coating material
US5320909A (en) * 1992-05-29 1994-06-14 United Technologies Corporation Ceramic thermal barrier coating for rapid thermal cycling applications
US5514482A (en) * 1984-04-25 1996-05-07 Alliedsignal Inc. Thermal barrier coating system for superalloy components
US5624721A (en) * 1995-05-08 1997-04-29 Alliedsignal Inc. Method of producing a superalloy article
US5683825A (en) * 1996-01-02 1997-11-04 General Electric Company Thermal barrier coating resistant to erosion and impact by particulate matter
EP0845547A1 (en) 1996-11-30 1998-06-03 ROLLS-ROYCE plc A thermal barrier coating for a superalloy article and a method of application thereof
US5817372A (en) 1997-09-23 1998-10-06 General Electric Co. Process for depositing a bond coat for a thermal barrier coating system
US5912087A (en) * 1997-08-04 1999-06-15 General Electric Company Graded bond coat for a thermal barrier coating system

Patent Citations (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3928026A (en) * 1974-05-13 1975-12-23 United Technologies Corp High temperature nicocraly coatings
US4248940A (en) * 1977-06-30 1981-02-03 United Technologies Corporation Thermal barrier coating for nickel and cobalt base super alloys
US4471017A (en) 1981-09-23 1984-09-11 Battelle-Institut E.V. High-temperature and thermal-shock-resistant thermally insulating coatings on the basis of ceramic materials
US4481237A (en) * 1981-12-14 1984-11-06 United Technologies Corporation Method of applying ceramic coatings on a metallic substrate
US4503130A (en) 1981-12-14 1985-03-05 United Technologies Corporation Prestressed ceramic coatings
US4446199A (en) 1982-07-30 1984-05-01 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Overlay metallic-cermet alloy coating systems
US4451496A (en) 1982-07-30 1984-05-29 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Coating with overlay metallic-cermet alloy systems
US5514482A (en) * 1984-04-25 1996-05-07 Alliedsignal Inc. Thermal barrier coating system for superalloy components
US4966820A (en) 1988-05-06 1990-10-30 Hitachi, Ltd. Ceramics-coated heat resisting alloy member
US5209645A (en) 1988-05-06 1993-05-11 Hitachi, Ltd. Ceramics-coated heat resisting alloy member
EP0340791A2 (en) 1988-05-06 1989-11-08 Hitachi, Ltd. Ceramics-coated heat resisting alloy member
US5320909A (en) * 1992-05-29 1994-06-14 United Technologies Corporation Ceramic thermal barrier coating for rapid thermal cycling applications
US5305726A (en) * 1992-09-30 1994-04-26 United Technologies Corporation Ceramic composite coating material
US5624721A (en) * 1995-05-08 1997-04-29 Alliedsignal Inc. Method of producing a superalloy article
US5683825A (en) * 1996-01-02 1997-11-04 General Electric Company Thermal barrier coating resistant to erosion and impact by particulate matter
EP0845547A1 (en) 1996-11-30 1998-06-03 ROLLS-ROYCE plc A thermal barrier coating for a superalloy article and a method of application thereof
US5912087A (en) * 1997-08-04 1999-06-15 General Electric Company Graded bond coat for a thermal barrier coating system
US5817372A (en) 1997-09-23 1998-10-06 General Electric Co. Process for depositing a bond coat for a thermal barrier coating system

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
A.A. Kodentsov et al., "High Temperature Nitridation of Ni-Cr Alloys," Metallurgical and Materials Transactions A, vol. 27A, No. 1, Jan. 1996, pp. 59-69.
Brandle, W. et al., Characteristics of Alumina Scales Formed on HVOF-Sprayed McrAIY Coatings, Proceedings of the 1998 25th International Conference on Metallurgical Coatings and Thin Films, in Surf Coat Technol: Oct. 10, 1998, vol. 108-109, pp. 10-15 Elsevier Science, S.A. Lausanne, Switzerland.
O. Knotek et al., "Diffusion Barrier Coatings With Active Bonding, Designed For Gas Turbine Blades," Surface and Coatings Technology, 68/69 (1994), pp. 22-26.

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US7264887B2 (en) 2002-01-10 2007-09-04 Alstom Technology Ltd. MCrAlY bond coating and method of depositing said MCrAlY bond coating
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US6817860B2 (en) 2002-03-15 2004-11-16 Catacel Corp. Catalytic combustor with improved light-off characteristics
US20030175633A1 (en) * 2002-03-15 2003-09-18 Whittenberger William A. Catalytic combustor with improved light-off characteristics
US20040021240A1 (en) * 2002-07-31 2004-02-05 Hancun Chen Ceramic manufacture for a composite ion transport membrane
US7338624B2 (en) 2002-07-31 2008-03-04 Praxair Technology Inc. Ceramic manufacture for a composite ion transport membrane
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US7390583B2 (en) * 2003-01-06 2008-06-24 Nhk Spring Co., Ltd. Sprayed coating and production method for the same
US6887589B2 (en) 2003-04-18 2005-05-03 General Electric Company Nickel aluminide coating and coating systems formed therewith
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US20050042461A1 (en) * 2003-08-18 2005-02-24 Honeywell International Inc. Diffusion barrier coating for si-based components
US7300702B2 (en) 2003-08-18 2007-11-27 Honeywell International, Inc. Diffusion barrier coating for Si-based components
US20050079368A1 (en) * 2003-10-08 2005-04-14 Gorman Mark Daniel Diffusion barrier and protective coating for turbine engine component and method for forming
US20070020399A1 (en) * 2003-10-08 2007-01-25 Gorman Mark D Diffusion barrier and protective coating for turbine engine component and method for forming
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US7172820B2 (en) 2003-11-25 2007-02-06 General Electric Company Strengthened bond coats for thermal barrier coatings
US20050112398A1 (en) * 2003-11-25 2005-05-26 Ramgopal Darolia Strengthened bond coats for thermal barrier coatings
US20050241148A1 (en) * 2004-04-28 2005-11-03 Siemens Westinghouse Power Corporation Thermally insulating layer incorporating a distinguishing agent and method for inspecting the same
US7334330B2 (en) 2004-04-28 2008-02-26 Siemens Power Generation, Inc. Thermally insulating layer incorporating a distinguishing agent and method for inspecting the same
US8313794B2 (en) 2004-04-28 2012-11-20 Siemens Energy, Inc. Thermally insulating layer incorporating a distinguishing agent
US20080131699A1 (en) * 2004-04-28 2008-06-05 Siemens Power Generation, Inc. Thermally insulating layer incorporating a distinguishing agent
US20060014032A1 (en) * 2004-07-16 2006-01-19 Florian Lampmann Thermal spray coating process and thermal spray coating materials
US7306860B2 (en) 2004-07-30 2007-12-11 Honeywell International, Inc. Protective coating for oxide ceramic based composites
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